CAJ | 학술논문

民用航空发动机双级高压涡轮二级叶片冷却用气通常引自高压压气机中间级，某些成熟发动机如GE90涡轮二级转子叶片的供气系统流路中，使用了减涡器结构以降低压力损失。本文介绍压气机盘腔管式减涡器引气系统，包括减涡器原理、减涡器结构等，重点分析了不同管长、不同引气鼓筒孔以及不同进口周向速度下气流的流动特性，并将三维分析结果与一维分析结果进行对比。通过分析得到，减涡管在一定管长下，流动损失最小。鼓筒孔形状、主流参数对最佳管长均存在影响。
민용항공발동궤쌍급고압와륜이급협편냉각용기통상인자고압압기궤중간급，모사성숙발동궤여GE90와륜이급전자협편적공기계통류로중，사용료감와기결구이강저압력손실。본문개소압기궤반강관식감와기인기계통，포괄감와기원리、감와기결구등，중점분석료불동관장、불동인기고통공이급불동진구주향속도하기류적류동특성，병장삼유분석결과여일유분석결과진행대비。통과분석득도，감와관재일정관장하，류동손실최소。고통공형상、주류삼수대최가관장균존재영향。
Turbine blade cooling air of aero-engine is bleed from high pressure compressor , which flow into blade through core engine inside.Vortex Reducer bleed system is introduced in this paper , which contain theory of vortex Reducer and structure of vortex reduc-er.The flow characteristic in Different length of tubes , bleed holes and tangential velocity is analyzed emphasis .The results of 3D and 1D are compared in this paper .As a result, flow loss is minimum in optimal tube length of vortex reducer .The optimal tube length is different in different hole form and mainstream parameter .